Rocket devices



O ,1963 L. D. ABERG 3,105,438

ROQKET- DEVICES Filed Nov. 21, 1950 N X 29- g E &: 8 5

J 2K v 29% I I INVENTOR 6 1 By LABS DQlf GLAS ABERG ATTORNEYS United States Patent 3,105,438 ROCKET DEVICES Lars Douglas Aberg, Goteborg, Sweden, assignor to The present invention relates to rocket devices of the type used for signalling and other purposes. More particularly the invention relates to rocket devices comprising an outer container and a rocket casing adapted to be expelled from said container, and a useful load, such as light signal device, in said casing and connected by cords or lines with a foldable parachute.

An object of the invention is to provide the rocket device in such a manner that a relatively short length and small volume of this device is obtained.

Another object of the invention is to provide a rocket having excellent flight stability.

Still another object of the invention is to provide an improved connection between the useful load and the suspension cords connecting said load to the parachute.

Other objects of the invention are made clear by the following description with reference to the accompanying drawing showing as example 'a rocket device according to the invention. FIG. 1 is an axial section of the rocket device, and FIG. 2 is a side view of a shell for the useful load and the parachute device for suspension of said shell and load after these parts have been expelled from the rocket casing.

In the drawing, 1 indicates a tubular outer container, 2 indicates a cap closing the bottom end of said tubular container Whereas 3 indicates a cap closing the top end of the same container. The container 1 as well as the caps 2 and 3 are cylindrical and have a circular crosssection. The end portions 4 and 5 respectively of the tubular container 1 have reduced cross-sections so that any level d-iiferences are not present in the joints 2 and 5 between the caps and the container. Owing to this fact, said joints may be effectively sealed by means of tapes sized to the parts. Said tapes are not shown in the drawing. The bottom or rear end of the container 1 is closed by a bottom plate 6 with an axial guide-socket 7 for a striking pin 8. The firing mechanism comprises a metal wire or spring 9 which by means of a screw ltlis fastened to the bottom plate 6 whereas the opposite free end of the wire or spring is inserted in a diametrical bore 11 in the lower end portion of the striking pin. By an angular rotation of the cap 2 the spring 9 is drawn out from engagement with the bore 11 after which the firing pin spring 12 is free to force said pin for initial firing of the percussion cap or primer 13. This cap or primer is inserted in a washer or ring 13 which together with the primer covers the outlet opening of a jet tube 14 for the combustion gases of the rocket fuel 18. The primer may be enclosed by a cover 15 of plastic or wax cloth sealing the opening of the jet tube and preventing removal of the primer 13 and washer 13 from the opening of said tube. From the narrow intermediate portion 14- the jet tube widens rearwardly With relatively small cone angle and has a fore portion 16 with a larger cone angle. The

33%,433 Patented Get. 1, 1963 ice latter portion 16 is connected to the rear end of a cylindrical or tubular motor housing 17 containing solid rocket fuel or powder 18. The motor housing 17 is partially inserted into and attached to the rear end portion of the cylindrical or tubular rocket casing 19 which above or in front of the motor housing 17 contains a tubular or cylindrical shell 29 disposed coaxially to the casing 19 and the tube 1 and enclosing the useful load consisting, for example, of anilluminatin-g composition 21. Between this composition and the fuel body 18 for expelling and propelling the rocket a composition id is fitted, said composition forming a delay fuse in the releasing of the shell 20 with the illuminating composition 21 from the racket casing 19.

In order to improve the flight properties of the rocket it may be provided with a guide fin device consisting, for example, of a plurality of blades 25 of steel projecting from a hub on the jet tube or nozzle 14. This hub is formed by two rings or washers 26 between which the inner ends of the blades 25 are clamped. These blades constitute a guiding and stabilizing factor especially in the start when such a factor is most required. After leaving the container 1 the resilient blades 25 will be straight and project radially from the hub 26 but as the speed of the rocket and the air resistance increases the blades by this resistance will be bent toward the position shown in FIG. 1.

The tubular shell 20 for the illuminating composition 21 has substantially smaller outer diameter than the inner diameter of the rocket casing 19 so that an annular space 22 will be provided bet-ween the parts 19 and 29. A supporting ring 23 is attached to the shell 20 and separated from the delay fuse 18 by packing rings 24 of felt or other suitable material, and in front of said supporting ring a folded parachute 27 of cloth, plastic or the like is stowed in the space 22. In front of this parachute and behind a second supporting ring 28 attached to the shell 20 cords or lines 29 are Wound round the shell 20 said cords or lines connecting the corners of the parachute with the fore or top end of the shell 21 The stowed parachute and the cords occupy substantially the entire annular space 22. Contrary to prior rockets, in which the parachute of cloth or the like with suspension cords is stowed in front or rear of the case or shell 2d, the parachute and cords in the rocket device according to the invention do not contribute to any increase of the length of the rocket. Thus a relatively short rocket will be obtained which is favourable from the point of view of stabilization.

' When the parachute and the cords are provided in the rocket as herein proposed, the parachute upon launching will be folded up normally.

A further factor supporting the stabilization is a (la-ml ing device connecting the parachute suspension cords 29 with the useful load or shell 20. Said damping device by preference comprises two springs 30 in the rform of plane spirals which are formed of a single wire, such as galvanized soft iron wire, said spirals at the outer periphery running into each other. In the centre of the rear or lower spiral the wire has a rear extension forming a foot 31 which by plastic 32 or other means is fixed to the top end of the shell 20 or the useful load 21. The opposite end portion of the wire extending from the centre of the spiral spring forms an eye or loop 33 to positioned between said motor case and one end of said shell, and a metal spring attached to and positioned on another end of said shell and connected to said suspension cords.

References Cited in the file of this patent UNITED STATES PATENTS 1,947,834 Dr-iggs et a1 Feb. 20, 1934 2,112,614 Wiley Mar. 29, 1938 2,785,632 Olauser et al. Mar. 19, 1957 3,015,274 Papesh Jan, 2, 1962 

1. A ROCKET DEVICE COMPRISING AN OUTER CONTAINER, A TUBULAR ROCKET CASING IN SAID CONTAINER, A MOTOR CASE CONTAINING A PROPULSION CHARGE POSITIONED IN AND CLOSING THE LOWER END OF SAID ROCKET CASING, MEAND WITHIN SAID OUTER CONTAINER TO IGNITE SAID PROPULSION CHARGE, A SHELL POSITIONED AGAINST AND ABOVE SAID MOTOR CASE WITHIN SAID ROCKET CASING, SAID SHELL HAVING AN OUTER DIAMETER WHICH IS SUBSTANTIALLY SMALLER THAN THE INNER DIAMETER OF SAID ROCKET CASING PROVIDING AN ANNULAR SPACE BETWEEN SAID SHELL AND SAID ROCKET CASING, A FOLDABLE PARACHUTE, SUSPENSION CORDS CONNECTING THE PARACHUTE TO THE UPPER END OF SAID SHELL, AN ILLUMINATING COMPOSITION SUBSTANTIALLY FILLING SAID SHELL, SAID ANNULAR SPACE CONTAINING SAID PARACHUTE AND CORDS IN STOWED CONDITION, AND PYROTECHNIC MEANS FOR LAUNCHING SAID SHELL WITH ILLUMINATING COMPOSITION, PARACHUTE AND SUSPENSION CORDS FROM SAID ROCKET CASING AND FOR IGNITING SAID COMPOSITION AT THE END OF THE COMBUSTION OF SAID PROPULSION CHARGE. 